Ge Avio S.r.l.

Avio Polska Sp. Z O.o

Enrico Ganzitti

Matteo Renato Usseglio

Tomasz Mucha

Gianfranco Brandino

Rafal Robak

A gas turbine engine including a frame assembly; a turbine assembly; and a nozzle disposed in the turbine assembly, wherein the nozzle defines an inner end along a radial direction and an outer end along the radial direction, wherein the outer end of the nozzle is supported by the frame assembly, wherein the inner end of the nozzle is supported by the frame assembly, and wherein the inner end of the nozzle is displaceable relative to the frame assembly in at least the radial direction.

Gas turbine engine nozzles

An apparatus for turbine engine including a turbine section with at least one turbine stage having a stationary vane assembly and a rotating blade assembly with combustion gases flowing through the turbine stage in a fore to aft direction. An interface is formed between a portion of the outer casing and a portion of the stationary vane assembly defining a leak flow path (LFP) where a seal is placed to retard combustion gases in the leak path.

Growing community of inventors

Turin, Italy

Enrico Ganzitti